高转速下航空柱塞泵动态特性研究

Aircraft piston pump is the key hydraulic component which ensures the safety of the aircraft flight. Increasing the rotation speed of the pump is the important way of improving its power density. However high speed has brought many scientific challenges to pump design, the traditional design theory of the piston pump has no longer met the requirements of high speed piston pump. Aiming to establish the design theory of the high speed pump under complicated working condition, the following basic research contents will be carried out: Firstly, stability of the rotating components of the pump under the high centrifugal and inertial force are studied. Secondly, Dynamic characteristics of the displacement control components under high speed are carried out, and key parameters such as the lateral inclination angle of wash plate will be optimized. Thirdly, characteristics of oil absorption of the pump at high speed are studied, and the absorption auxiliary function of the centrifugal turbine for the pump is discussed. Fourthly, the frequency and amplitude of pressure pulsation of the pump under the wide speed range is analyzed, the integrated pressure pulsation attenuator will be developed. Fifthly, characteristics of the oil film bearing of the friction pairs under coupling of the high speed, wide temperature, and high pressure is analyzed, and parameters of friction pairs under high speed is optimized. Sixthly, the performance test of the high speed aircraft piston pump prototype is carried out. The project will provide a strong theoretical and technical support for localization of the aircraft piston pump for the large aircraft project as soon as possible.

航空柱塞泵是保证飞机安全飞行的关键液压动力元件，提高柱塞泵旋转速度是提高柱塞泵功率密度的一种重要方式。高转速对柱塞泵设计带来了诸多科学挑战，传统的柱塞泵设计理论已不能满足高转速航空柱塞泵的工作要求。本项目针对复杂工况下的高转速柱塞泵，开展以下基础性研究：1.分析高转速下柱塞泵旋转组件离心力和惯性力对其稳定性的影响规律。2.分析高转速下柱塞泵排量控制组件的动力学特性，优化斜盘横向倾角等参数。3.分析高转速对柱塞腔吸油特性的影响规律，讨论离心增压涡轮对柱塞泵的吸油辅助作用。4.分析转速大范围变化下柱塞泵压力脉动频率和幅值的变化规律，设计内置式压力脉动衰减器。5.分析高转速与宽温、高压耦合作用下的摩擦副油膜承载特性，提出高转速下摩擦副参数优化方法。6.高转速航空柱塞泵试验研究。本项目将为高转速航空柱塞泵建立一套完整的设计理论，为大飞机项目航空柱塞泵的早日国产化提供强有力的理论和技术支持。

航空柱塞泵是飞机液压系统的核心元件，为了提高液压系统的能量密度，航空柱塞泵正逐步向高转速方向发展，因此研究高转速下柱塞泵的动态特性对于研制高可靠航空柱塞泵具有重要意义。.本项目研究成果包括：建立了包含缸体-柱塞-滑靴的柱塞泵旋转组件的动力学模型，研究了高转速下旋转组件的离心力对其动力学特性及泵轴受力产生的影响；建立高转速柱塞泵的排量控制组件动力学模型，对排量组件进行了结构参数分析；开展了高转速柱塞泵吸油特性分析，建立柱塞泵的全气蚀模型，设计新型阻尼槽，显著抑制气蚀现象；设计了离心增压涡轮，改善柱塞泵在高转速下的吸油特性；对高转速柱塞泵振动机理进行分析，提出一种新型压力脉动衰减器以降低压力脉动；基于高转速柱塞泵配流副的受力情况，建立配流副油膜压力的数学模型，进行配流副油膜特性的动力学分析，并研究压力、转速、温度对油膜压力的影响；设计了高速泵试验台并进行试验研究。.本项目研究成果为：发表学术论文12篇，申请或授权发明专利5项；相关成果应用获得中国航空学会科学技术一等奖1项